82 FR 32622 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 135 (July 17, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 135 (July 17, 2017)
| Page Range | 32622-32626 | |
| FR Document | 2017-14469 |
[Federal Register Volume 82, Number 135 (Monday, July 17, 2017)] [Rules and Regulations] [Pages 32622-32626] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-14469] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9567; Directorate Identifier 2016-NM-147-AD; Amendment 39-18955; AD 2017-14-11] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2007-13-08, for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2007-13-08 required repetitive inspections of the auxiliary power unit (APU) starter motor, APU inlet plenum, and APU air intake for discrepancies; repetitive cleaning of the APU air intake; and applicable corrective actions. This AD expands the applicability of AD 2007-13-08, and includes an optional terminating installation for the repetitive actions. This AD was prompted by a determination that the unsafe condition could occur on additional airplanes. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 21, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 21, 2017. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of July 25, 2007 (72 FR 33877, June 20, 2007). ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office-EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@ [[Page 32623]] airbus.com; Internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-9567. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 9567; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800- 647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2007-13-08, Amendment 39-15112 (72 FR 33877, June 20, 2007) (``AD 2007-13-08''). AD 2007-13-08 applied to certain Airbus Model A318, A319, A320, and A321 series airplanes. The NPRM published in the Federal Register on January 6, 2017 (82 FR 1623). The NPRM was prompted by a determination that the unsafe condition could occur on additional airplanes. The NPRM proposed to continue to require repetitive inspections of the APU starter motor, APU inlet plenum, and APU air intake for discrepancies; repetitive cleaning of the APU air intake; and applicable corrective actions. We are issuing this AD to detect and correct reverse flow during APU startup, which could lead to flame propagation in the APU air inlet and intake duct. Such conditions could result in an in-flight fire in the APU area. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016-0176, dated August 31, 2016; corrected September 1, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A318, A319, A320, and A321 airplanes. The MCAI states: An operator reported black smoke at the rear of the fuselage during taxi after landing. The smoke was caused by a fire in the auxiliary power unit (APU) air intake. The subsequent analysis demonstrated that, following numerous unsuccessful APU start attempts in flight, there is a risk of reverse flow leading to flame propagation to the APU air inlet and air intake duct. This condition, if not detected and corrected, could result in an in-flight fire in the APU area. Prompted by these findings, Airbus issued Service Bulletin (SB) A320-49-1068 to provide inspection and cleaning instructions. The applicable Flight Crew Operating Manual (FCOM) already contained a limitation for the number of APU start attempts, as follows: APU STARTER After 3 starter motor duty cycles, wait 60 minutes before attempting 3 more cycles To address this potential unsafe condition, EASA issued AD 2006- 0153 to require repetitive inspections of the APU starter motor, APU inlet plenum and APU air intake [for discrepancies], as well as repetitive cleaning of the APU air intake [and applicable corrective actions]. As the reverse flow inside the APU can only occur in flight with the APU inlet closed, various modifications (mod) were developed to introduce a new electronic control box (ECB) with associated software, the functionality of which keeps the APU inlet door open for 15 minutes, following an APU auto-shutdown in flight. Consequently, AD 2006-0153 [which corresponds to FAA AD 2007-13-08], was revised reducing the Applicability by excluding certain post-mod aeroplanes, and introducing these modifications as optional terminating actions. After EASA AD 2006-0153R2 was issued, it was determined that, as an APU ECB can be replaced (or moved from one aeroplane to another) in service, inadvertently installing a pre-mod ECB would reintroduce the unsafe condition. Prompted by this finding, EASA issued AD 2016- 0159, retaining the requirements of EASA AD 2006-0153R2, which was superseded, expanding the Applicability and including references to additional optional terminating actions. Since EASA AD 2016-0159 was issued, it was determined that paragraph (5) of the [EASA] AD contained some erroneous statements, inadvertently excluding certain aeroplanes, those that have Airbus mod 23698 or mod 24498 embodied in production, from the repetitive actions. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2016-0159, which is superseded, and corrects paragraph (5). For post-mod aeroplanes where, inadvertently, an `affected' ECB has been installed in service, this AD adds the requirement to restore those aeroplanes to post-mod configuration by installation of a `serviceable' ECB. This [EASA] AD also introduces some editorial changes, not affecting the required actions. This [EASA] AD is republished as it was determined that one `affected' and one `non-affected' ECB were inadvertently omitted in the Tables. Discrepancies include a defective APU starter motor, misaligned brush wear indicator-pin, oil contamination of the brush wear indicator, and dirt, debris, dust, sand, oil, combustible residues, grease and other contaminations of the APU inlet plenum. Corrective actions include replacement of the APU starter motor and cleaning the APU air intake, if necessary. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-9567. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Support for the NPRM United Airlines and Air Line Pilots Association, International, stated their support for the content of the NPRM. Request To Include Missing Part Number Airbus asked that electronic control box (ECB) part number (P/N) 3888394-230300 for APU GTCP36-300 be added to table 1 to paragraph (g) of the proposed AD. Airbus stated that the part number is missing in the table. We agree with the commenter's request. We have added ECB P/N 3888394-230300 for APU GTCP36-300 to table 1 to paragraphs (g), (h), (i)(2)(ii), (j), and (k) of this AD. That part number was omitted from EASA AD 2016-0176, dated August 31, 2016; however, EASA issued a correction, which added that part number, on September 1, 2016. We have also included the corrected EASA AD in this final rule. Request To Provide Retrofit Installation Method and Interchangeability Information Virgin America asked that the proposed AD requirements provide an approved retrofit installation method for P/N 3888394-321206. Virgin America also asked that the proposed AD requirements clearly state the interchangeability or lack of [[Page 32624]] interchangeability for the part numbers identified in table 2 of the proposed AD. Virgin America stated that it receives the Airbus Illustrated Parts Catalog (IPC) on a quarterly basis, which it regularly corrects to remove interchangeability. Virgin America added that in addition to correcting the IPC every quarter, it has repeatedly requested that Airbus Airworthiness and Engineering synchronize their viewpoint of how the IPC is intended to be utilized by operators. Virgin America noted that since EASA has corresponding ADs, it would mean that no ECB can be considered ``interchangeable'' by Airbus, since accomplishing a service bulletin is not the same as accomplishing an airplane maintenance manual. Virgin America requested this coordination within Airbus, both from an ever increasing manpower requirement (i.e., the more ADs, the more IPCs that need interchangeability monitored and removed quarterly) and also from a parts support request, since some parts providers use the IPC as the means to pool and issue parts. Virgin America concluded that a separate pool of non-interchangeable parts adds significantly to the cost impact of the proposed AD. We acknowledge the commenter's concerns; however, an approved retrofit installation method and interchangeability of part numbers are not addressed by this AD. While there might be merit to the commenter's suggestions, this AD is not the appropriate document in which to evaluate those suggestions. Therefore, we have not changed this AD in this regard. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information, which describes procedures for replacing the ECB. These documents are distinct since they apply to different airplane models in different configurations. Airbus Service Bulletin A320-49-1077, Revision 04, dated February 27, 2013. Airbus Service Bulletin A320-49-1098, dated June 21, 2011. Airbus Service Bulletin A320-49-1102, dated January 3, 2012. Airbus Service Bulletin A320-49-1107, Revision 02, dated May 10, 2016. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 1,182 airplanes of U.S. registry. The actions required by AD 2007-13-08, and retained in this AD, take about 4 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 2007-13-08 is $340 per product. We also estimate that it will take about 4 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $401,880, or $340 per product. We have received no definitive data that will enable us to provide cost estimates for the on-condition actions specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2007-13-08, Amendment 39-15112 (72 FR 33877, June 20, 2007), and adding the following new AD: 2017-14-11 Airbus: Amendment 39-18955; Docket No. FAA-2016-9567; Directorate Identifier 2016-NM-147-AD. (a) Effective Date This AD is effective August 21, 2017. (b) Affected ADs This AD replaces AD 2007-13-08, Amendment 39-15112 (72 FR 33877, June 20, 2007) (``AD 2007-13-08''). (c) Applicability This AD applies to Airbus airplanes identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD, all manufacturer serial numbers, certificated in any category. (1) Model A318-111, -112, -121, and -122 airplanes. (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes. (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 49, Airborne Auxiliary Power. [[Page 32625]] (e) Reason This AD was prompted by a report of a fire in the auxiliary power unit (APU) air intake. An analysis demonstrated that, following numerous unsuccessful APU start attempts in flight, there is a risk of reverse flow, which could lead to flame propagation to the APU air inlet and air intake duct. This AD was also prompted by the determination that AD 2007-13-08 only addresses the unsafe condition for certain airplanes. We are issuing this AD to detect and correct reverse flow during APU startup, which could lead to flame propagation in the APU air inlet and intake duct. Such conditions could result in an in-flight fire in the APU area. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections and Corrective Actions Except as provided by paragraph (i) of this AD, within 600 flight hours after July 25, 2007 (the effective date of AD 2007-13- 08), or within 60 days after the effective date of this AD, whichever occurs later: Inspect the APU starter motor, APU air inlet plenum, and APU air intake of each affected APU identified in table 1 to paragraphs (g), (h), (i)(2)(ii), (j), and (k) of this AD for discrepancies; and do all applicable corrective actions before further flight; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-49-1068, Revision 01, dated February 2, 2006. Repeat the inspection thereafter at intervals not to exceed 600 flight hours. Table 1 to Paragraphs (g), (h), (i)(2)(ii), (j), and (k) of This AD-- Affected APU and Electronic Control Box (ECB) ------------------------------------------------------------------------ APU ECB part Nos. (P/N) ------------------------------------------------------------------------ APIC APS 3200..................... 4500003D, 4500003E, 4500003F, 4500003G, 4500003H, or 4500003J. Honeywell 131-9A.................. 3888394-120201, 3888394-121202, 3888394-121203, 3888394-221202, or 3888394-221203. Honeywell GTCP36-300.............. 307950-1, 307950-2, 307950-3, 307950- 4, 304640-1, 304640-2, 304640-3, 304640-4, 304817-1, 304817-2, or 3888394-230300. ------------------------------------------------------------------------ (h) Repetitive Cleanings Except as provided by paragraph (i) of this AD, prior to the accumulation of 2,400 flight hours since first flight of the airplane, or within 600 flight hours after July 25, 2007 (the effective date of AD 2007-13-08), or within 60 days after the effective date of this AD, whichever occurs latest, unless accomplished previously in accordance with Airbus Service Bulletin A320-49-1098, dated June 21, 2011: Clean the APU air intake of each affected APU identified in table 1 to paragraphs (g), (h), (i)(2)(ii), (j), and (k) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-49-1068, Revision 01, dated February 2, 2006. Repeat the cleaning task thereafter at intervals not to exceed 2,400 flight hours. (i) Exceptions to Requirements in Paragraphs (g) and (h) of This AD (1) For airplanes equipped with an APU and associated ECB part number identified in table 2 to paragraphs (i)(1), (i)(2)(ii), and (j) of this AD, the actions specified in paragraphs (g) and (h) of this AD are not required. Table 2 to Paragraphs (i)(1), (i)(2)(ii), and (j) of This AD--Non- Affected ECB ------------------------------------------------------------------------ APU ECB Part Nos. (P/N) ------------------------------------------------------------------------ APIC APS 3200..................... 4500003K, 4500003L, or 4500003M. Honeywell 131-9A.................. 3888394-121204, 3888394-121205, 3888394-221204, 3888394-221205, or 3888394-321206. Honeywell GTCP36-300.............. 304640-5, 304817-3, or 3888394- 230301. ------------------------------------------------------------------------ (2) For airplanes on which Airbus Modification 35803, 35936, 152289, 152645, 155015, or 157848 has been embodied in production, the actions specified in paragraphs (g) and (h) of this AD are not required provided that, within 30 days after the effective date of this AD, the applicable actions specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD are done. (i) The part number of the installed ECB is identified. (ii) Any affected ECB identified in table 1 to paragraphs (g), (h), (i)(2)(ii), (j), and (k) of this AD that is found to be installed is replaced with an ECB having a part number identified in table 2 to paragraphs (i)(1), (i)(2)(ii), and (j) of this AD, as applicable to the APU installed on the airplane; and the replacement is done in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (i)(2)(ii)(A), (i)(2)(ii)(B), (i)(2)(ii)(C), (i)(2)(ii)(D), (i)(2)(ii)(E), or (i)(2)(ii)(F) of this AD; or using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or the European Aviation Safety Agency (EASA), or Airbus's EASA Design Organization Approval (DOA). (A) Airbus Service Bulletin A320-49-1070, dated July 28, 2006. (B) Airbus Service Bulletin A320-49-1075, Revision 01, dated December 1, 2006. (C) Airbus Service Bulletin A320-49-1077, Revision 04, dated February 27, 2013. (D) Airbus Service Bulletin A320-49-1098, dated June 21, 2011. (E) Airbus Service Bulletin A320-49-1102, dated January 3, 2012. (F) Airbus Service Bulletin A320-49-1107, Revision 02, dated May 10, 2016. (3) For airplanes on which an APU ECB having a part number approved after the effective date of this AD is installed, the actions specified in paragraphs (g) and (h) of this AD are not required, provided the conditions specified in paragraphs (i)(3)(i) and (i)(3)(ii) of this AD are met. (i) The part number must be approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (ii) The installation must be accomplished in accordance with airplane modification instructions approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (j) Optional Terminating Action Replacing an affected ECB identified in table 1 to paragraphs (g), (h), (i)(2)(ii), (j), and (k) of this AD with an ECB having a part number identified in table 2 to paragraphs (i)(1), (i)(2)(ii), and (j) of this AD, as applicable to the APU installed on the airplane, constitutes terminating action for the repetitive inspections required by paragraphs (g) and (h) of this AD. The replacement must be done in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (i)(2)(ii)(A), (i)(2)(ii)(B), (i)(2)(ii)(C), (i)(2)(ii)(D), (i)(2)(ii)(E), or (i)(2)(ii)(F) of this AD, or using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (k) Parts Installation Prohibition As of the effective date of this AD, no person may install on any airplane an APU with an associated ECB identified in table 1 to paragraphs (g), (h), (i)(2)(ii), (j), and (k) of this AD. [[Page 32626]] (l) Credit for Previous Actions This paragraph provides credit for actions specified in paragraphs (i)(2) and (j) of this AD, if those actions were performed before the effective date of this AD using any of the service information specified in paragraphs (l)(1) through (l)(7) of this AD. (1) Airbus Service Bulletin A320-49-1075, dated September 22, 2006, which was incorporated by reference in AD 2007-13-08. (2) Airbus Service Bulletin A320-49-1077, dated March 21, 2007, which is not incorporated by reference in this AD. (3) Airbus Service Bulletin A320-49-1077, Revision 01, dated August 9, 2007, which is not incorporated by reference in this AD. (4) Airbus Service Bulletin A320-49-1077, Revision 02, dated July 1, 2008, which is not incorporated by reference in this AD. (5) Airbus Service Bulletin A320-49-1077, Revision 03, dated December 8, 2008, which is not incorporated by reference in this AD. (6) Airbus Service Bulletin A320-49-1107, dated November 5, 2013, which is not incorporated by reference in this AD. (7) Airbus Service Bulletin A320-49-1107, Revision 01, dated July 28, 2015, which is not incorporated by reference in this AD. (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Branch, send it to the attention of the person identified in paragraph (n)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (ii) AMOCs approved previously for AD 2007-13-08 are approved as AMOCs for the corresponding provisions of paragraphs (g) and (h) of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016-0176, dated August 31, 2016; corrected September 1, 2016, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-9567. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-1405; fax 425-227-1149. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(5) and (o)(6) of this AD. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on August 21, 2017. (i) Airbus Service Bulletin A320-49-1077, Revision 04, dated February 27, 2013. (ii) Airbus Service Bulletin A320-49-1098, dated June 21, 2011. (iii) Airbus Service Bulletin A320-49-1102, dated January 3, 2012. (iv) Airbus Service Bulletin A320-49-1107, Revision 02, dated May 10, 2016. (4) The following service information was approved for IBR on July 25, 2007 (72 FR 33877, June 20, 2007). (i) Airbus Service Bulletin A320-49-1068, Revision 01, dated February 2, 2006. (ii) Airbus Service Bulletin A320-49-1070, dated July 28, 2006. (iii) Airbus Service Bulletin A320-49-1075, Revision 01, dated December 1, 2006. (5) For service information identified in this AD, contact Airbus, Airworthiness Office-EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; Internet: http://www.airbus.com. (6) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on June 29, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-14469 Filed 7-14-17; 8:45 am] BILLING CODE 4910-13-P
![32622 Federal Register / Vol. 82, No. 135 / Monday, July 17, 2017 / Rules and Regulations
(f) Compliance (2) Contacting the Manufacturer: For any the availability of this material at NARA, call
Comply with this AD within the requirement in this AD to obtain corrective 202–741–6030, or go to: http://
compliance times specified, unless already actions from a manufacturer, the action must www.archives.gov/federal-register/cfr/ibr-
done. be accomplished using a method approved locations.html.
by the Manager, New York ACO, ANE–170,
(g) Replacement Issued in Renton, Washington, on July 6,
FAA; or TCCA; or the TCCA DAO. If
2017.
Before the accumulation of 7,500 total approved by the DAO, the approval must
include the DAO-authorized signature. Dionne Palermo,
flight cycles, or within 10 days after the
effective date of this AD, whichever occurs (3) Reporting Requirements: A federal Acting Manager, Transport Airplane
later, do the actions required by paragraphs agency may not conduct or sponsor, and a Directorate, Aircraft Certification Service.
(g)(1) through (g)(4) of this AD, in accordance person is not required to respond to, nor [FR Doc. 2017–14698 Filed 7–14–17; 8:45 am]
with the Accomplishment Instructions of shall a person be subject to a penalty for BILLING CODE 4910–13–P
Bombardier Service Bulletin 100–53–32, failure to comply with a collection of
dated February 16, 2017. information subject to the requirements of
(1) Remove the fasteners attaching the the Paperwork Reduction Act unless that
DEPARTMENT OF TRANSPORTATION
machined center fitting (part number collection of information displays a current
1005340715), wing-to-fuselage attachment valid OMB Control Number. The OMB
Federal Aviation Administration
and splice fitting at fuselage station 587, to Control Number for this information
the rear spar frame lower flange splice. collection is 2120–0056. Public reporting for
(2) Do a general visual inspection of the this collection of information is estimated to 14 CFR Part 39
fasteners for damage and an eddy current be approximately 5 minutes per response, [Docket No. FAA–2016–9567; Directorate
inspection of the fastener holes for damage. including the time for reviewing instructions, Identifier 2016–NM–147–AD; Amendment
(3) Rework the fastener holes as applicable. completing and reviewing the collection of 39–18955; AD 2017–14–11]
(4) Replace the fasteners with self-aligning information. All responses to this collection
fasteners and self-aligning collars. of information are mandatory. Comments RIN 2120–AA64
concerning the accuracy of this burden and
(h) Exception to Service Information suggestions for reducing the burden should Airworthiness Directives; Airbus
Specifications be directed to the FAA at: 800 Independence Airplanes
If any damage of any fastener hole is found Ave. SW., Washington, DC 20591, Attn:
during any inspection required by paragraph Information Collection Clearance Officer, AGENCY: Federal Aviation
(g)(2) of this AD, before further flight, repair AES–200. Administration (FAA), Department of
using a method approved by the Manager, Transportation (DOT).
New York Aircraft Certification Office (ACO), (k) Related Information
ACTION: Final rule.
ANE–170, FAA; or Transport Canada Civil (1) Refer to Mandatory Continuing
Aviation (TCCA); or Bombardier, Inc.’s TCCA Airworthiness Information (MCAI) Canadian
SUMMARY: We are superseding
Design Approval Organization (DAO). Airworthiness Directive CF–2017–12, dated
March 10, 2017, for related information. You Airworthiness Directive (AD) 2007–13–
(i) Reporting may examine the MCAI on the Internet at 08, for certain Airbus Model A318,
Submit a report of the findings of the http://www.regulations.gov by searching for A319, A320, and A321 series airplanes.
inspections required by paragraph (g)(2) of and locating Docket No. FAA–2017–0696. AD 2007–13–08 required repetitive
this AD, as specified in Appendix 1 of (2) For more information about this AD, inspections of the auxiliary power unit
Bombardier Service Bulletin 100–53–32, contact Aziz Ahmed, Airframe Engineer, (APU) starter motor, APU inlet plenum,
dated February 16, 2017, to bbad_challenger_ Airframe and Mechanical Systems Branch, and APU air intake for discrepancies;
stress@aero.bombardier.com, at the ANE–171, FAA, New York ACO, 1600 repetitive cleaning of the APU air
applicable time specified in paragraph (i)(1) Stewart Avenue, Suite 410, Westbury, NY
intake; and applicable corrective
or (i)(2) of this AD. 11590; telephone: 516–228–7329; fax: 516–
(1) If the inspection was done on or after 794–5531. actions. This AD expands the
the effective date of this AD: Submit the applicability of AD 2007–13–08, and
report within 10 days after the inspection. (l) Material Incorporated by Reference includes an optional terminating
(2) If the inspection was done before the (1) The Director of the Federal Register installation for the repetitive actions.
effective date of this AD: Submit the report approved the incorporation by reference This AD was prompted by a
within 10 days after the effective date of this (IBR) of the service information listed in this determination that the unsafe condition
AD. paragraph under 5 U.S.C. 552(a) and 1 CFR could occur on additional airplanes. We
part 51.
(j) Other FAA AD Provisions are issuing this AD to address the unsafe
(2) You must use this service information
The following provisions also apply to this as applicable to do the actions required by condition on these products.
AD: this AD, unless this AD specifies otherwise. DATES: This AD is effective August 21,
(1) Alternative Methods of Compliance (i) Bombardier Service Bulletin 100–53–32, 2017.
(AMOCs): The Manager, New York ACO, dated February 16, 2017. The Director of the Federal Register
ANE–170, FAA, has the authority to approve (ii) Reserved. approved the incorporation by reference
AMOCs for this AD, if requested using the (3) For service information identified in of certain publications listed in this AD
procedures found in 14 CFR 39.19. In this AD, contact Bombardier, Inc., 400 Côte-
as of August 21, 2017.
accordance with 14 CFR 39.19, send your Vertu Road West, Dorval, Québec H4S 1Y9,
request to your principal inspector or local Canada; telephone: 514–855–5000; fax: 514– The Director of the Federal Register
Flight Standards District Office, as 855–7401; email: thd.crj@ approved the incorporation by reference
appropriate. If sending information directly aero.bombardier.com; Internet: http:// of certain other publications listed in
to the New York ACO, send it to ATTN: www.bombardier.com. this AD as of July 25, 2007 (72 FR
Program Manager, Continuing Operational (4) You may view this service information 33877, June 20, 2007).
jstallworth on DSK7TPTVN1PROD with RULES
Safety, FAA, New York ACO, 1600 Stewart at the FAA, Transport Airplane Directorate, ADDRESSES: For service information
Avenue, Suite 410, Westbury, NY 11590; 1601 Lind Avenue SW., Renton, WA. For
identified in this final rule, contact
telephone 516–228–7300; fax 516–794–5531. information on the availability of this
Before using any approved AMOC, notify material at the FAA, call 425–227–1221. Airbus, Airworthiness Office–EIAS, 1
your appropriate principal inspector, or (5) You may view this service information Rond Point Maurice Bellonte, 31707
lacking a principal inspector, the manager of that is incorporated by reference at the Blagnac Cedex, France; telephone: +33 5
the local flight standards district office/ National Archives and Records 61 93 36 96; fax: +33 5 61 93 44 51;
certificate holding district office. Administration (NARA). For information on email: account.airworth-eas@
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![Federal Register / Vol. 82, No. 135 / Monday, July 17, 2017 / Rules and Regulations 32623
airbus.com; Internet: http:// for the Member States of the European aeroplanes where, inadvertently, an ‘affected’
www.airbus.com. You may view this Union, has issued EASA AD 2016–0176, ECB has been installed in service, this AD
referenced service information at the dated August 31, 2016; corrected adds the requirement to restore those
aeroplanes to post-mod configuration by
FAA, Transport Airplane Directorate, September 1, 2016 (referred to after this
installation of a ‘serviceable’ ECB. This
1601 Lind Avenue SW., Renton, WA. as the Mandatory Continuing [EASA] AD also introduces some editorial
For information on the availability of Airworthiness Information, or ‘‘the changes, not affecting the required actions.
this material at the FAA, call 425–227– MCAI’’), to correct an unsafe condition This [EASA] AD is republished as it was
1221. It is also available on the Internet for all Airbus Model A318, A319, A320, determined that one ‘affected’ and one ‘non-
at http://www.regulations.gov by and A321 airplanes. The MCAI states: affected’ ECB were inadvertently omitted in
searching for and locating Docket No. An operator reported black smoke at the the Tables.
FAA–2016–9567. rear of the fuselage during taxi after landing. Discrepancies include a defective
The smoke was caused by a fire in the APU starter motor, misaligned brush
Examining the AD Docket
auxiliary power unit (APU) air intake. The wear indicator-pin, oil contamination of
You may examine the AD docket on subsequent analysis demonstrated that,
the brush wear indicator, and dirt,
the Internet at http:// following numerous unsuccessful APU start
attempts in flight, there is a risk of reverse debris, dust, sand, oil, combustible
www.regulations.gov by searching for
flow leading to flame propagation to the APU residues, grease and other
and locating Docket No. FAA–2016–
air inlet and air intake duct. contaminations of the APU inlet
9567; or in person at the Docket This condition, if not detected and plenum. Corrective actions include
Management Facility between 9 a.m. corrected, could result in an in-flight fire in replacement of the APU starter motor
and 5 p.m., Monday through Friday, the APU area. and cleaning the APU air intake, if
except Federal holidays. The AD docket Prompted by these findings, Airbus issued necessary. You may examine the MCAI
contains this AD, the regulatory Service Bulletin (SB) A320–49–1068 to
provide inspection and cleaning instructions.
in the AD docket on the Internet at
evaluation, any comments received, and
The applicable Flight Crew Operating http://www.regulations.gov by searching
other information. The address for the for and locating Docket No. FAA–2016–
Docket Office (telephone 800–647–5527) Manual (FCOM) already contained a
limitation for the number of APU start 9567.
is Docket Management Facility, U.S.
attempts, as follows:
Department of Transportation, Docket Comments
APU STARTER
Operations, M–30, West Building We gave the public the opportunity to
After 3 starter motor duty cycles, wait 60
Ground Floor, Room W12–140, 1200 minutes before attempting 3 more cycles participate in developing this AD. The
New Jersey Avenue SE., Washington, following presents the comments
To address this potential unsafe condition,
DC 20590. EASA issued AD 2006–0153 to require received on the NPRM and the FAA’s
FOR FURTHER INFORMATION CONTACT: repetitive inspections of the APU starter response to each comment.
Sanjay Ralhan, Aerospace Engineer, motor, APU inlet plenum and APU air intake
International Branch, ANM–116, [for discrepancies], as well as repetitive Support for the NPRM
Transport Airplane Directorate, FAA, cleaning of the APU air intake [and United Airlines and Air Line Pilots
1601 Lind Avenue SW., Renton, WA applicable corrective actions].
As the reverse flow inside the APU can
Association, International, stated their
98057–3356; telephone 425–227–1405; support for the content of the NPRM.
only occur in flight with the APU inlet
fax 425–227–1149. closed, various modifications (mod) were Request To Include Missing Part
SUPPLEMENTARY INFORMATION: developed to introduce a new electronic Number
control box (ECB) with associated software,
Discussion the functionality of which keeps the APU Airbus asked that electronic control
We issued a notice of proposed inlet door open for 15 minutes, following an box (ECB) part number (P/N) 3888394–
rulemaking (NPRM) to amend 14 CFR APU auto-shutdown in flight. Consequently, 230300 for APU GTCP36–300 be added
part 39 to supersede AD 2007–13–08, AD 2006–0153 [which corresponds to FAA to table 1 to paragraph (g) of the
AD 2007–13–08], was revised reducing the
Amendment 39–15112 (72 FR 33877, proposed AD. Airbus stated that the part
Applicability by excluding certain post-mod
June 20, 2007) (‘‘AD 2007–13–08’’). AD aeroplanes, and introducing these number is missing in the table.
2007–13–08 applied to certain Airbus modifications as optional terminating We agree with the commenter’s
Model A318, A319, A320, and A321 actions. request. We have added ECB P/N
series airplanes. The NPRM published After EASA AD 2006–0153R2 was issued, 3888394–230300 for APU GTCP36–300
in the Federal Register on January 6, it was determined that, as an APU ECB can to table 1 to paragraphs (g), (h), (i)(2)(ii),
2017 (82 FR 1623). The NPRM was be replaced (or moved from one aeroplane to (j), and (k) of this AD. That part number
prompted by a determination that the another) in service, inadvertently installing a was omitted from EASA AD 2016–0176,
unsafe condition could occur on pre-mod ECB would reintroduce the unsafe dated August 31, 2016; however, EASA
condition. Prompted by this finding, EASA
additional airplanes. The NPRM issued a correction, which added that
issued AD 2016–0159, retaining the
proposed to continue to require requirements of EASA AD 2006–0153R2, part number, on September 1, 2016. We
repetitive inspections of the APU starter which was superseded, expanding the have also included the corrected EASA
motor, APU inlet plenum, and APU air Applicability and including references to AD in this final rule.
intake for discrepancies; repetitive additional optional terminating actions.
Request To Provide Retrofit Installation
cleaning of the APU air intake; and Since EASA AD 2016–0159 was issued, it
was determined that paragraph (5) of the Method and Interchangeability
applicable corrective actions. We are
[EASA] AD contained some erroneous Information
issuing this AD to detect and correct
jstallworth on DSK7TPTVN1PROD with RULES
reverse flow during APU startup, which statements, inadvertently excluding certain Virgin America asked that the
aeroplanes, those that have Airbus mod
could lead to flame propagation in the proposed AD requirements provide an
23698 or mod 24498 embodied in
APU air inlet and intake duct. Such production, from the repetitive actions. approved retrofit installation method for
conditions could result in an in-flight For the reason described above, this P/N 3888394–321206. Virgin America
fire in the APU area. [EASA] AD retains the requirements of EASA also asked that the proposed AD
The European Aviation Safety Agency AD 2016–0159, which is superseded, and requirements clearly state the
(EASA), which is the Technical Agent corrects paragraph (5). For post-mod interchangeability or lack of
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![32624 Federal Register / Vol. 82, No. 135 / Monday, July 17, 2017 / Rules and Regulations
interchangeability for the part numbers • Airbus Service Bulletin A320–49– the national government and the States,
identified in table 2 of the proposed AD. 1077, Revision 04, dated February 27, or on the distribution of power and
Virgin America stated that it receives 2013. responsibilities among the various
the Airbus Illustrated Parts Catalog (IPC) • Airbus Service Bulletin A320–49– levels of government.
on a quarterly basis, which it regularly 1098, dated June 21, 2011. For the reasons discussed above, I
corrects to remove interchangeability. • Airbus Service Bulletin A320–49– certify that this AD:
Virgin America added that in addition 1102, dated January 3, 2012. 1. Is not a ‘‘significant regulatory
to correcting the IPC every quarter, it • Airbus Service Bulletin A320–49– action’’ under Executive Order 12866;
1107, Revision 02, dated May 10, 2016. 2. Is not a ‘‘significant rule’’ under the
has repeatedly requested that Airbus
This service information is reasonably DOT Regulatory Policies and Procedures
Airworthiness and Engineering
available because the interested parties (44 FR 11034, February 26, 1979);
synchronize their viewpoint of how the
have access to it through their normal 3. Will not affect intrastate aviation in
IPC is intended to be utilized by
course of business or by the means Alaska; and
operators. Virgin America noted that 4. Will not have a significant
since EASA has corresponding ADs, it identified in the ADDRESSES section.
economic impact, positive or negative,
would mean that no ECB can be Costs of Compliance on a substantial number of small entities
considered ‘‘interchangeable’’ by We estimate that this AD affects 1,182 under the criteria of the Regulatory
Airbus, since accomplishing a service airplanes of U.S. registry. Flexibility Act.
bulletin is not the same as The actions required by AD 2007–13–
accomplishing an airplane maintenance List of Subjects in 14 CFR Part 39
08, and retained in this AD, take about
manual. Virgin America requested this 4 work-hours per product, at an average Air transportation, Aircraft, Aviation
coordination within Airbus, both from labor rate of $85 per work-hour. Based safety, Incorporation by reference,
an ever increasing manpower on these figures, the estimated cost of Safety.
requirement (i.e., the more ADs, the the actions that are required by AD
more IPCs that need interchangeability Adoption of the Amendment
2007–13–08 is $340 per product.
monitored and removed quarterly) and We also estimate that it will take Accordingly, under the authority
also from a parts support request, since about 4 work-hours per product to delegated to me by the Administrator,
some parts providers use the IPC as the comply with the basic requirements of the FAA amends 14 CFR part 39 as
means to pool and issue parts. Virgin this AD. The average labor rate is $85 follows:
America concluded that a separate pool per work-hour. Based on these figures,
of non-interchangeable parts adds we estimate the cost of this AD on U.S. PART 39—AIRWORTHINESS
significantly to the cost impact of the operators to be $401,880, or $340 per DIRECTIVES
proposed AD. product. ■ 1. The authority citation for part 39
We acknowledge the commenter’s We have received no definitive data continues to read as follows:
concerns; however, an approved retrofit that will enable us to provide cost
installation method and estimates for the on-condition actions Authority: 49 U.S.C. 106(g), 40113, 44701.
interchangeability of part numbers are specified in this AD. § 39.13 [Amended]
not addressed by this AD. While there
Authority for This Rulemaking ■ 2. The FAA amends § 39.13 by
might be merit to the commenter’s
suggestions, this AD is not the Title 49 of the United States Code removing Airworthiness Directive (AD)
appropriate document in which to specifies the FAA’s authority to issue 2007–13–08, Amendment 39–15112 (72
evaluate those suggestions. Therefore, rules on aviation safety. Subtitle I, FR 33877, June 20, 2007), and adding
we have not changed this AD in this section 106, describes the authority of the following new AD:
regard. the FAA Administrator. ‘‘Subtitle VII: 2017–14–11 Airbus: Amendment 39–18955;
Aviation Programs,’’ describes in more Docket No. FAA–2016–9567; Directorate
Conclusion detail the scope of the Agency’s Identifier 2016–NM–147–AD.
We reviewed the available data, authority. (a) Effective Date
including the comments received, and We are issuing this rulemaking under
This AD is effective August 21, 2017.
determined that air safety and the the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701: (b) Affected ADs
public interest require adopting this AD
with the changes described previously General requirements.’’ Under that This AD replaces AD 2007–13–08,
and minor editorial changes. We have section, Congress charges the FAA with Amendment 39–15112 (72 FR 33877, June
promoting safe flight of civil aircraft in 20, 2007) (‘‘AD 2007–13–08’’).
determined that these changes:
air commerce by prescribing regulations
• Are consistent with the intent that (c) Applicability
for practices, methods, and procedures
was proposed in the NPRM for This AD applies to Airbus airplanes
the Administrator finds necessary for identified in paragraphs (c)(1), (c)(2), (c)(3),
correcting the unsafe condition; and
safety in air commerce. This regulation and (c)(4) of this AD, all manufacturer serial
• Do not add any additional burden is within the scope of that authority numbers, certificated in any category.
upon the public than was already because it addresses an unsafe condition (1) Model A318–111, –112, –121, and –122
proposed in the NPRM. that is likely to exist or develop on airplanes.
Related Service Information Under 1 products identified in this rulemaking (2) Model A319–111, –112, –113, –114,
action. –115, –131, –132, and –133 airplanes.
CFR Part 51
jstallworth on DSK7TPTVN1PROD with RULES
(3) Model A320–211, –212, –214, –231,
Airbus has issued the following Regulatory Findings –232, and –233 airplanes.
service information, which describes We determined that this AD will not (4) Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
procedures for replacing the ECB. These have federalism implications under
documents are distinct since they apply Executive Order 13132. This AD will (d) Subject
to different airplane models in different not have a substantial direct effect on Air Transport Association (ATA) of
configurations. the States, on the relationship between America Code 49, Airborne Auxiliary Power.
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(l) Credit for Previous Actions by searching for and locating Docket No. DEPARTMENT OF TRANSPORTATION
This paragraph provides credit for actions FAA–2016–9567.
specified in paragraphs (i)(2) and (j) of this (2) For more information about this AD, Federal Aviation Administration
AD, if those actions were performed before contact Sanjay Ralhan, Aerospace Engineer,
the effective date of this AD using any of the International Branch, ANM–116, Transport 14 CFR Part 39
service information specified in paragraphs Airplane Directorate, FAA, 1601 Lind
(l)(1) through (l)(7) of this AD. [Docket No. FAA–2017–0021; Directorate
Avenue SW., Renton, WA 98057–3356;
(1) Airbus Service Bulletin A320–49–1075, Identifier 2017–NE–01–AD; Amendment 39–
telephone 425–227–1405; fax 425–227–1149. 18951; AD 2017–14–07]
dated September 22, 2006, which was
(3) Service information identified in this
incorporated by reference in AD 2007–13–08. RIN 2120–AA64
(2) Airbus Service Bulletin A320–49–1077, AD that is not incorporated by reference is
dated March 21, 2007, which is not available at the addresses specified in
paragraphs (o)(5) and (o)(6) of this AD. Airworthiness Directives; International
incorporated by reference in this AD.
(3) Airbus Service Bulletin A320–49–1077, Aero Engines AG Turbofan Engines
(o) Material Incorporated by Reference
Revision 01, dated August 9, 2007, which is AGENCY: Federal Aviation
not incorporated by reference in this AD. (1) The Director of the Federal Register
approved the incorporation by reference
Administration (FAA), DOT.
(4) Airbus Service Bulletin A320–49–1077,
Revision 02, dated July 1, 2008, which is not (IBR) of the service information listed in this ACTION: Final rule.
incorporated by reference in this AD. paragraph under 5 U.S.C. 552(a) and 1 CFR
(5) Airbus Service Bulletin A320–49–1077, part 51.
SUMMARY: We are adopting a new
Revision 03, dated December 8, 2008, which (2) You must use this service information
airworthiness directive (AD) for certain
is not incorporated by reference in this AD.
as applicable to do the actions required by
International Aero Engines AG (IAE)
(6) Airbus Service Bulletin A320–49–1107, V2522–A5, V2524–A5, V2527–A5,
dated November 5, 2013, which is not this AD, unless this AD specifies otherwise.
(3) The following service information was V2527E–A5, V2527M–A5, V2530–A5,
incorporated by reference in this AD. V2533–A5, V2525–D5, V2528–D5, and
(7) Airbus Service Bulletin A320–49–1107, approved for IBR on August 21, 2017.
Revision 01, dated July 28, 2015, which is (i) Airbus Service Bulletin A320–49–1077, V2531–E5 turbofan engines. This AD
not incorporated by reference in this AD. Revision 04, dated February 27, 2013. was prompted following a self-
(ii) Airbus Service Bulletin A320–49–1098, disclosure by IAE regarding
(m) Other FAA AD Provisions manufacturing quality escapes. This AD
dated June 21, 2011.
The following provisions also apply to this (iii) Airbus Service Bulletin A320–49– requires replacing the affected and
AD: suspect parts within the time limits
1102, dated January 3, 2012.
(1) Alternative Methods of Compliance specified in the compliance section. We
(AMOCs): The Manager, International (iv) Airbus Service Bulletin A320–49–
1107, Revision 02, dated May 10, 2016. are issuing this AD to address the unsafe
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to (4) The following service information was condition on these products.
approve AMOCs for this AD, if requested approved for IBR on July 25, 2007 (72 FR DATES: This AD is effective August 21,
using the procedures found in 14 CFR 39.19. 33877, June 20, 2007). 2017.
In accordance with 14 CFR 39.19, send your (i) Airbus Service Bulletin A320–49–1068, The Director of the Federal Register
request to your principal inspector or local Revision 01, dated February 2, 2006. approved the incorporation by reference
Flight Standards District Office, as (ii) Airbus Service Bulletin A320–49–1070, of certain publications listed in this AD
appropriate. If sending information directly dated July 28, 2006. as of August 21, 2017.
to the manager of the International Branch, (iii) Airbus Service Bulletin A320–49–
send it to the attention of the person ADDRESSES: For service information
1075, Revision 01, dated December 1, 2006. identified in this final rule, contact
identified in paragraph (n)(2) of this AD.
(5) For service information identified in
Information may be emailed to: 9-ANM-116- International Aero Engines AG, 400
AMOC-REQUESTS@faa.gov. this AD, contact Airbus, Airworthiness
Main Street, East Hartford, CT 06118;
(i) Before using any approved AMOC, Office–EIAS, 1 Rond Point Maurice Bellonte,
phone: 860–565–0140; email: help24@
notify your appropriate principal inspector, 31707 Blagnac Cedex, France; telephone: +33
pw.utc.com; Internet: http://
or lacking a principal inspector, the manager 5 61 93 36 96; fax: +33 5 61 93 44 51; email:
fleetcare.pw.utc.com. You may view this
of the local flight standards district office/ account.airworth-eas@airbus.com; Internet:
certificate holding district office. The AMOC service information at the FAA, Engine
http://www.airbus.com.
approval letter must specifically reference (6) You may view this service information
& Propeller Directorate, 1200 District
this AD. at the FAA, Transport Airplane Directorate,
Avenue, Burlington, MA. For
(ii) AMOCs approved previously for AD 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
2007–13–08 are approved as AMOCs for the
information on the availability of this material at the FAA, call 781–238–7125.
corresponding provisions of paragraphs (g) It is also available on the Internet at
material at the FAA, call 425–227–1221.
and (h) of this AD. http://www.regulations.gov by searching
(2) Contacting the Manufacturer: As of the (7) You may view this service information
that is incorporated by reference at the for and locating Docket No. FAA–2017–
effective date of this AD, for any requirement
National Archives and Records 0021.
in this AD to obtain corrective actions from
a manufacturer, the action must be Administration (NARA). For information on Examining the AD Docket
accomplished using a method approved by the availability of this material at NARA, call
the Manager, International Branch, ANM– 202–741–6030, or go to: http:// You may examine the AD docket on
116, Transport Airplane Directorate, FAA; or www.archives.gov/federal-register/cfr/ibr- the Internet at http://
EASA; or Airbus’s EASA DOA. If approved locations.html. www.regulations.gov by searching for
by the DOA, the approval must include the and locating Docket No. FAA–2017–
DOA-authorized signature. Issued in Renton, Washington, on June 29, 0021; or in person at the Docket
jstallworth on DSK7TPTVN1PROD with RULES
2017. Management Facility between 9 a.m.
(n) Related Information
Michael Kaszycki, and 5 p.m., Monday through Friday,
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD Acting Manager, Transport Airplane except Federal holidays. The AD docket
2016–0176, dated August 31, 2016; corrected Directorate, Aircraft Certification Service. contains this final rule, the regulatory
September 1, 2016, for related information. [FR Doc. 2017–14469 Filed 7–14–17; 8:45 am] evaluation, any comments received, and
This MCAI may be found in the AD docket BILLING CODE 4910–13–P other information. The address for the
on the Internet at http://www.regulations.gov Docket Office (phone: 800–647–5527) is
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Document Created: 2017-07-15 03:46:05
Document Modified: 2017-07-15 03:46:05
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective August 21, 2017. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. | |
| FR Citation | 82 FR 32622 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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